Yuzhnoye State Design Office named after M.K.Yangel was founded in 1954 to initiate development of strategic-purpose missile-weapon complexes.

More than 50 years of collaboration with PA Yuzhny Machine-Building Plant, academic, science and research, manufacturing enterprises of former Soviet Union resulted in the development and production of four generations of strategic missiles, represented by 13 modifications which formed the basis of strategic missile forces. There were also produced 7 types of world-class launch vehicles (Kosmos, Interkosmos, Cyclone-2, Cyclone-3, Zenit-2, Zenit-3SL, Dnepr).

SDO YUZHNOYE’S ORGANIZATION CHARTGeneral Designer – General Director

Dr. Stanislav Konyukhov

First Deputy General Designer –General Director

Mr. Alexander Mashchenko

First Deputy General Director –Chief Engineer

Mr. Vladimir Vasilina

Deputy General Designer on

Scientific work

Dr. Perlik

Deputy GeneralDesigner on Propulsion

SystemsMr. Shnyakin

Deputy General Designer on testing and operations

Mr. Agarkov

Deputy General Designer on

Management and CoordinationMr. Kuryachiy

Deputy General Designer on personnel

Mr. Novikov

Deputy General Designer on Information Resources

Mr. Polyakov

Heads of Design Offices, Divisions and Departments

Analysis Division

Ballistics, Aerodynamics,

Heat, Mass

Design Division

Development of Space Launch Vehicles and

Missiles Complexes

Design Division

Manufacture Drawings

Documentation for Launch

Vehicles and Missiles

Design Division

Development of Space Systems and satellites; Telemetry and

Communications Equipment

Design Division

Development of Actuators,

Special Systems and Assemblies

Analysis and Experimental

Testing Division

Structural Strength of Units,

Subsystems and systems of Launch

Vehicles and Missiles

Design Division

Development of Liquid\Solid Propellant

Engines and Pyrotechnics

Experimental Testing Division

Power Supply Systems and

Liquid Propellant Propulsion Systems

Finalizing

Material Development

Division

Testing of Manufacture Technology,

Material Research and

Analysis

Design Supervision

and Operations

Division

Design Division

Conversion Activities

Civil Products

Development

Preparation and Support

Division

Research work and

Experimental Finalizing

Division

Administration, Planning,

Coordination of works, technical and economic analysis and

financial accounting

Marketing and Foreign Economic

Affairs Division

Department

Scientific and engineering information; patent and

license research

Division

Preparation, Classification,

Coding, Registration

and Storage of Design

Documentation

First Deputy General Designer –General Director

System Design and Business DevelopmentDr. Alexander Degtyarev

SPACE-ROCKET TECHNOLOGYSYSTEM DESIGN AND DEVELOPMENT

ROCKET-SPACE COMPLEXESIncluding

LAUNCH VEHICLES

SPACE SYSTEMSIncluding

Upper Stages

Fuel Systems

Rocket Body Sections

Liquid and Solid-Propellant Rocket Engines

Aerodynamic Fairings

Actuators and Special Systems

Software Support

Experimental-Test Works

Support of Works Performed by Participating Institutions on Ground Complexes, Propulsion Systems, Control Systems, Measurement Systems and other Systems of Rockets and Spacecraft

SPACECRAFT

Platforms

Actuators, Mechanisms

Propulsion Systems

Thermostatic Control Systems

Antenna-Feeder and Antenna-Waveguide Devices

Onboard Switchgear Equipment

Launch Complex and its Infrastructure

Processing Complex and its Infrastructure

Assembly, Integration and Test Facilities

Over 50 years of experience in designing, developing and manufacturing rocket-space and spacecraft technologies;

Rich experience in International cooperation with leading European, American, Asian and Arabic aerospace companies and organizations;

Wide and long-term established cooperation with the leading Ukrainian and Russian aerospace companies, organizations and representatives of other industries;

Experienced in cooperation under International Standards within the frames of different International Programs;

COMPETITIVE ADVANTAGES

COMPETITIVE ADVANTAGES

Flexible in applying and adapting standards required by a Customer/ Contractual Terms and Conditions;

Possesses a complete technological cycle starting from designingspacecraft up to the launch of spacecraft using launch-vehicles of its own development;

Active in developing and commercializing new space and civil application technologies;

Competitive pricing policy;

Open for new directions of cooperation;

Reliable and experienced Partner for new and already establishedpartnership.

Quality Management - ISO 9001-2000;

Flexible in applying and adapting Standards required by Customers/ Contractual terms and Conditions;

Rich experience in cooperation with International Partners under such programs as SEA LAUNCH Program, VEGA LV Program and etc.

STANDARDS AND CERTIFICATION

73 enterprise standards regulating various types of SDO Yuzhnoye’s activity;

SDO Yuzhnoye’s Quality Management System complies with the requirements of the

International Standard ISO 9001:2000, its Ukrainian (DSTU ISO 9001-2001) and

Russian (GOST R ISO 9001-2001) analogues.

LAUNCH FACILITIES

Plesetsk

Baikonur

Platform Odyssey

Cyclone 2

DneprZenit 2

Cyclone 3

Zenit 3SL

Railroad Launch (SS-24)Air Based Launch

Dniepropetrovsk

PROSPECTIVE LAUNCH SYSTEMSIn the nearest time Yuzhnoye will be able to propose newly developed launch vehicles for providing customers with reliable launch services. The new systems are Zenit-3SLB and Zenit-2SLB (launch services will be provided by the Land Launch Joint Stock Company) and Cyclone-4 (launch services will be provided by Alcantara Cyclone Space Joint Stock Company).

CYCLONE-4

Lift-off mass, t (without PL)

9

7.9101.5

±5±0.05…0.08

303

3191

UDMH

49121

NTO

Number of stages

Propellant componentsOxidizerFuel

Propellant mass, t1st Stage2nd Stage3rd Stage

Vacuum thrust

1st Stage2nd Stage3rd Stage

Injection accuracy

On altitude, kmOn inclination, deg

for Hcirc=500 km, i=90º:

of engines, tf

5.0 (perigee)On altitude, kmfor GTO:

±0.05…0.08On inclination, deg100 (apogee)

0

1000

2000

3000

4000

5000

6000

2000 3000 4400 6000 8000Hcirc, km

Gpl

, kg

PAYLOAD CAPABILITIESPAYLOAD CAPABILITIES

Launch site: Alcantara (Brazil)

Launch site has convenient geographical position and provides wide range of launch azimuths

Performance capability for GTO is: 1600 kg (Alcantara, i=5.1 degrees)

MAYAK FAMILY LAUNCH VEHICLES

Launch mass, t 130 185 250 320 375

# of stages/boosters 2/0 2/4 2/0 3/0 3/4Payload mass, kg:

Hcirc=200km, i=5002800

4500 6400 8800 11500

H=150/35860 km, i=2.10-

1300 1800 3000 3800

ROCKET ENGINES DEVELOPED BY YUZHNOYE

The achieved level of reliability

The achieved level The achieved level of reliabilityof reliability

For Liquid Rocket Engines no less than0,992-0,999

For Liquid Rocket Engines For Liquid Rocket Engines no less thanno less than0,9920,992--0,990,9999

For Solid propellant Rocket Motors

0,995-0,999

For Solid propellant For Solid propellant Rocket MotorsRocket Motors

0,9950,995--0,990,9999

More than 35 liquid rocket engines and liquid propulsion More than 35 liquid rocket engines and liquid propulsion systems have been developedsystems have been developed

A highly reliable engine cluster and propulsion system are A highly reliable engine cluster and propulsion system are designed for the Ndesigned for the N--1 Lunar Launch System. The propulsion 1 Lunar Launch System. The propulsion system ensures soft landing on the Moon surface and takesystem ensures soft landing on the Moon surface and take--off of the Moon, and insertion ofoff of the Moon, and insertion of the lunar vehicle into the the lunar vehicle into the lunar orbit. lunar orbit.

The engine cluster includes:The engine cluster includes:•• RDRD--858, a single858, a single--chamber dualchamber dual--mode main engine;mode main engine;•• RDRD--859, a two859, a two--chamber singlechamber single--mode backup engine. Each mode backup engine. Each engine ensures two burns.engine ensures two burns.

High reliability of the engines was proven by a large number High reliability of the engines was proven by a large number of ground tests. Total operating time is:of ground tests. Total operating time is:•• 253281 s for RD253281 s for RD--858; 858; •• 209463 s for RD209463 s for RD--859.859.

Three propulsion systems were successfully flightThree propulsion systems were successfully flight--tested in tested in the composition of the Earth artificial satellite.the composition of the Earth artificial satellite.

LIQUID ROCKET ENGINES RD858 AND

RD859 OF THE LUNAR MODULE

SDO YUZHNOYE IS CAPABLE OF INJECTING PAYLOADS INTO THE FLIGHT TRAJECTORY TO

THE MOON OR DIRECTLY INTO THE NEAR-MOON ORBIT USING ITS LAUNCH-VEHICLES

PAYLOAD CAPABILITIESPayload mass, kgILV

to the Moon into near-moon orbit

Zenit – 3SL 4200 ~1000*

Zenit – 3SLB 3900 ~1000*

Dnepr-1 with AST-1 500 200-250

* using orbital propulsion system (DU-802) as an adjusting and inhibiting propulsion system. In case of development of propulsion system modification with increased propellant reserve (~1000 kg) the mass of payload into near-moon orbit can be increased up to ~2500 kg for Zenit-3SL ILV and up to ~2300 kg for Zenit-3SLB ILV.

Propellants NTO+UDMHVacuum thrust, kgf

– main engine from 400 to 2250– backup engine 2045

Vacuum specific impulse, s– main engine 315– backup engine 312

Burn time, s– main engine up to 470 – backup engine up to 400

Engine cluster mass, kg 110Mixture ratio

– main engine from 1,6 to 2,03– backup engine 2,0

MAIN SPECIFICATIONS OF

THE ENGINES RD858 AND RD859

The Main Engine Assembly is a part of Liquid Propulsion System for Attitude Vernier Upper Module of the European Vega Launch Vehicle.

The MEA is developed under a Contract with Avio (Italy) on the basis of units from serially produced engines.

Purposes of the MEA are as follows:Thrust generation;Pitch/yaw control;Upper Module maneuvering;Upper Module deorbit.

Propellants NTO+UDMHVacuum thrust, kgf 250Vacuum specific impulse, s 315.5Number of burns 5

MAIN ENGINE ASSEMBLY

FOR THE EUROPEAN VEGA LV

Currently the Upper Stage for Ukrainian – Russian Dnepr LV has been designed and is now under intensive testing. A principally new propellants supply system was introduced with the use of Pneumopump Assembly (PPA). Utilization of PPA allows to increase power-mass characteristics, some of which cannot be reached by the existing propulsion systems.

Propellants:• Oxidizer NTO• Fuel UDMHPropellants mass, kg 250–500Dry mass, kg 165.4

•Vacuum specific impulse, s•- Main engines (ME) 322,5•- Thruster 243 •Vacuum thrust, kgf•- ME 450•- Thruster 11,1•Mixture rate 2,25 •Number of ME burns 10

DU802 PROPULSION SYSTEM

Propellants supply system has been tested (pressurization system, propellants tanks and PPA).

Working media:• Oxidizer NT• Fuel UDMH• Gas Helium• supplying pressure 25 - 70 kgf/cm2

Flow-rate:• oxidizer up to 1.1 kg/s• fuel up to 0.5 kg/s

Helium pressure 10-30 kgf/cm2

Helium temperature 450 К

Efficiency 0.75

The pneumopump unit is a component of DU 802 propulsion unit.

PNEUMOPUMP

The engine unit is a component of DU 802 liquid The engine unit is a component of DU 802 liquid propulsion systempropulsion system

Propellants NTO+UDMH

• Vacuum thrust, kgf 450• Vacuum specific impulse, s 322.5• Mixture ratio 2.25• Number of burns up to 10• Burn duration of a single run, s:• - max 350• - min 3• Total burn duration, s 350

ENGINE UNIT OF

DU802 PROPULSION SYSTEM

A phase of development tests has been accomplished

The engine RD861K is designed for generating thrust and ensuring control in pitch and yaw channels through an active leg of the Cyclone-4 LV third stage flight.

Propellants:- Oxidizer NTO- Fuel UDMH

Vacuum thrust, kgf 7916Vacuum specific impulse, s 330Mass, kg 207

Number of burns 3…5Total burn duration, s 450Length, mm 2000Diameter of nozzle exit, mm 1010

LIQUID ROCKET ENGINE RD861K

TEST BASE OF YUZHNOYE SDO

AND YUZHMASH PLANT

SDO Yuzhnoye is capable of performing firing tests of any engine with propellants NTO + UDMH and thrust of up to 120 tf, as well as engines with LOX + Kerosene and thrust of up to 100 tf.

SDO Yuzhnoye will soon be capable of performing tests of engineswith propellants LOX + Methane.

SATELLITES DEVELOPED BY YUZHNOYE

MS-2-8 “SICH-2” SATELLITE

The MS-2-8 satellite is designed for the Earth Remote Sensing with the use of mid-high resolution multi-band imager. In addition, the satellite provides store & forward messaging service

Mass, kg 160

Orbit:

- altitude, km 668

- inclination, deg 98

Wavelengths for imaging modes, μm:

- panchromatic 0.50-0.89

- multispectral 0.50-0.59; 0.61-0.68;0.79-0.89

Resolution in nadir, m 7.8 – pan; 30 – multi.

Swath width in nadir, km 46.6

Coverage area width, km ±500

Accuracy, deg. 0.2

Frequency band for store & forward communication payload, MHz:

- uplink 144…146

- downlink 435…438

Frequency band for payload, MHz 8 025 … 8 400

Frequency bands for radio-lines, MHz

2 025 … 2 1102 200 … 2 290